GB2558071A - Turbine for turbine engine - Google Patents
Turbine for turbine engine Download PDFInfo
- Publication number
- GB2558071A GB2558071A GB1718654.5A GB201718654A GB2558071A GB 2558071 A GB2558071 A GB 2558071A GB 201718654 A GB201718654 A GB 201718654A GB 2558071 A GB2558071 A GB 2558071A
- Authority
- GB
- United Kingdom
- Prior art keywords
- casing
- sectors
- turbine
- ring
- blades
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
- F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
- F01D11/125—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material with a reinforcing structure
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/246—Fastening of diaphragms or stator-rings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
- F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
- F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/11—Shroud seal segments
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A turbine 1 for a turbine engine which has a casing 2, there is a rotor comprising blades 29, and a sealing means 15 which extends around the rotor and is formed of multiple sectors or segments, the sealing means including an abradable material 16 layer which is located at the interface between the rotor and sealing means, the blades include wipers 31,32 which extend into a groove 17,19 in the sealing means such that the combination for a labyrinth seal, and where the combined assembly of the rotor and sealing means is installed into the casing through movement along the longitudinal axis of the engine only. There may be multiple wipers of varying lengths on the rotor blades. There may be multiple stages which comprise a combined rotor and sealing member. Also included is a claim to a method of assembling the combination of rotor and sealing member.
Description
(54) Title of the Invention: Turbine for turbine engine
Abstract Title: Turbine with segmented sealing member assembled around rotor (57) A turbine 1 for a turbine engine which has a casing 2, there is a rotor comprising blades 29, and a sealing means 15 which extends around the rotor and is formed of multiple sectors or segments, the sealing means including an abradable material 16 layer which is located at the interface between the rotor and sealing means, the blades include wipers 31,32 which extend into a groove 17,19 in the sealing means such that the combination for a labyrinth seal, and where the combined assembly of the rotor and sealing means is installed into the casing through movement along the longitudinal axis of the engine only. There may be multiple wipers of varying lengths on the rotor blades. There may be multiple stages which comprise a combined rotor and sealing member. Also included is a claim to a method of assembling the combination of rotor and sealing member.
Fig. 1
Fig. 3
Fig. 8
Fig. 9
ί i
Turbine for turbine engine
The present invention relates to a turbine for a turbine engine, in particular for an aircraft turbojet engine or turboprop engine, as well as a method for assembling such a turbine.
A turbine engine, in particular a twin-spool turbine engine, conventionally comprises, from upstream to downstream, a fan, a low-pressure compressor, a high-pressure compressor, a combustion chamber, a high-pressure turbine and a low-pressure turbine.
By convention, in the present application, the terms “upstream” and “downstream” are defined with respect to the direction of flow of air in the turbine engine. Likewise, by convention in the present application, the terms “interior” and “exterior”, “lower” and “upper” and “internal” and “external” are defined radially with respect to the axis of the turbine engine.
A low-pressure turbine of a turbine engine comprises a turbine shaft on which a plurality of successive stages are mounted, each comprising a bladed wheel and a nozzle. Each bladed wheel comprises a disc carrying at its external periphery blades coaxial with one another and with the shaft driving the rotor of the turbine by suitable means. Each nozzle comprises an internal annular platform and an external annular platform between which substantially radial vanes extend. The external platform of the nozzle comprises means for attachment and fixing on an external casing of the turbine. All the nozzles form the fixed part of the engine referred to as the stator.
The blades of each wheel of the rotor conventionally comprise wipers at their radially external periphery, cooperating with a ring of abradable material so as to form sealing means of the labyrinth seal type.
Such a structure is for example known from the document FR 2 879 649.
In order to guarantee high efficiency of the turbine engine, it is necessary to control the clearances at said seals and to limit leakage rates at the interface between the wipers of the blades and the ring made from abradable material.
There exists a need to further improve the efficacy of such labyrinth seals as well as the assembly of the turbine.
The aim of the invention is in particular to afford a simple, effective and economical solution to this problem.
To this end, the invention proposes a turbine for a turbine engine, in particular for an aircraft turbojet engine or turboprop engine, comprising a casing and a rotor comprising blades, the radially external periphery of which comprises at least one first wiper extending radially outwards, sealing means extending radially around the blades and comprising a ring made from abradable material, the radially external ends of the first wipers being engaged in a groove in said ring made from abradable material so as to form a seal of the labyrinth type, characterised in that said ring is formed by a plurality of contiguous annular sectors, each ring sector comprising at least one fixing member cooperating with at least one complementary attachment flange of the casing so as to provide the mounting of each sector on the casing by axial movement of said sector with respect to the casing. The casing is configured so as to allow the mounting of the sectors in the casing, solely by axial movement of said sectors.
In this way, the various sectors can be mounted around the blade so as to form the ring made from abradable material, before axially engaging the assembly comprising in particular the blades and said sectors in the casing, so that the members for fixing the sectors cooperate with the flanges with a view to providing the fixing of said sectors in the casing, around the blades.
Each groove comprises for example a radially external cylindrical surface and two lateral surfaces or flanks, extending radially.
The depth, that is to say the radial dimension, of each groove is for example between 0.5 and 5 mm.
In this case, it is possible to have a first wiper that forms a seal of the labyrinth type with the walls of the groove, said seal having a large pressure drop, substantially greater than in the case of the prior art. This is because it is possible to have a first wiper that has a large radial dimension, engaged in a groove also with a large radial dimension, the mounting then being made possible by the sectorised structure of the ring and by the axial engagement of said sectors and blades in the turbine casing.
Each flange may comprise a first part extending radially from a cylindrical or frustoconical wall of the casing, and a second part extending axially, cooperating with the fixing member of the corresponding ring sector.
Each fixing member may comprise a section roughly in a U shape comprising arms extending axially and radially separated from each other, engaging on either side of an axial part of the complementary attachment flange.
The turbine may comprise at least one first fixing member and at least one second fixing member, offset axially with respect to each other, able to cooperate respectively with a first flange and a second flange of the casing.
Each ring sector may comprise a block of abradable material fixed to a support, each fixing member being formed by said support or fixed to said support.
Each blade may comprise at least one first wiper extending radially and at least one second wiper extending radially outwards with respect to the first wiper, the first wiper and the second wiper being offset axially with respect to each other.
The first wiper may be engaged in a first groove in the corresponding ring sector, the second wiper being engaged in a second groove in the ring sector.
The first wiper may be engaged in a first groove in the corresponding ring sector, the radially external end of the second wiper being situated in the vicinity of a surface in a portion of a cylinder of the ring sector.
The turbine may comprise a nozzle, comprising a radially external platform, in abutment on a flange of the casing, the sector comprising a fixing member fixing the external platform of the nozzle to the corresponding flange of the casing, while providing the fixing of the sector on said flange.
The turbine may comprise a first blade stage and a second blade stage surrounded respectively by a first ring and a second ring made from abradable material and formed from sectors so as to form a first and second labyrinth seal, the casing being configured so as to allow the mounting of the sectors in the casing, solely by axial movement of said sectors.
The invention also relates to a method for assembling a turbine of the aforementioned type, characterised in that it comprises the steps consisting of:
- mounting the sectors around the blade so as to form the ring made from abradable material,
- axially engaging the assembly comprising in particular the blades and said sectors in the casing, so that the fixing members of the sectors cooperate with the flanges so as to provide the fixing of said sectors in the casing, around the blades.
Such a method is simple and quick to implement and allows easy assembly or dismantling of the turbine.
The method may comprise the steps consisting of:
- mounting a first ring of sectors around a first blade stage, and axially engaging the assembly comprising in particular said blades and said sectors in the casing, so that the fixing members of the sectors cooperate with the corresponding flanges so as to provide the fixing of said sectors in the casing, around said blades,
- mounting a second ring of sectors around a second blade stage, and axially engaging the assembly comprising in particular said blades and said sectors in the casing, so that the fixing members of the sectors cooperate with the corresponding flanges so as to provide the fixing of said sectors in the casing, around said blades.
The invention will be understood better and other details, features and advantages of the invention will emerge from a reading of the following description given by way of non-limitative example with reference to the accompanying drawings, in which:
- figure 1 is a view in axial section of a part of a turbine according to an embodiment of the invention,
- figure 2 is an exploded view, in perspective, of a part of the turbine,
- figures 3 and 5 illustrate various steps of assembling the turbine of figures 1 and 2,
- figure 6 illustrates a blade and an abradable sector of a turbine according to a variant embodiment of the invention,
- figures 7 to 13 illustrate various steps of assembling a turbine according to another embodiment of the invention.
A low-pressure turbine 1 of a turbine engine according to a first embodiment is illustrated in figure 1. The turbine 1 comprises a fixed casing 2, having a frustoconical wall 3 the axis of which corresponds to the axis of the turbine engine and from which flanges 4, 5 extend radially inwards. The casing 2 comprises in particular an upstream flange 4 and a downstream flange 5. The terms upstream and downstream are defined with respect to the direction of flow of the gas flow in the turbine 1, that is to say from left to right in figure 1.
Each flange 4, 5 comprises a first annular part 6 extending radially inwards from the frustoconical wall 3, and a second cylindrical part 7 extending in the downstream direction.
The upstream flange 4 further comprises an annular radial rim 8 extending radially inwards from the downstream end of the second part 7.
The stator of the turbine 1 comprises in particular a nozzle stage 9, referred to as the upstream nozzle. The nozzle 9 comprising a radially internal platform (not visible), a radially external platform 10 and fixed vanes 11 connecting said platforms.
The external platform 10 of the upstream nozzle 9 comprises a recess 12 delimiting a support zone formed by a radially external rim 13, extending axially in the downstream direction.
The downstream end of the rim 13 is in abutment axially on the rim 8 of the upstream flange 4 of the casing 2, said rim 13 further being in axial abutment on the second part 7 of the upstream flange 4.
The turbine 1 further comprises a ring 14 comprising an abradable material, mounted fixedly on the casing 2 and formed by a plurality of contiguous angular sectors 15, identical and distributed over the entire circumference. Each sector comprises a block of abradable material
16.
The ring formed by the various blocks 16 of abradable material comprises a first annular groove 17, having a first radial dimension or depth and emerging at a cylindrical radially internal surface 18 of the ring, and two second annular grooves 19, each having a second radial dimension or depth and emerging at said radially internal surface 18.
The first radial dimension is for example between 0.5 and 5 mm.
The second radial dimension is for example between 0.5 and mm.
The two second grooves 19 are offset axially on either side of the first groove 17.
The external surface of the block 16 of each sector 15 is fixed to an annular-shaped support 20.
An annular fixing member 21 with a U-shaped cross section is fixed at the upstream end of the support 20, radially inside said support 20. Said upstream fixing member 21 comprises a radially external arm 22, coming radially into abutment on the external surface of the second part 7 of the upstream flange 4, and a radially internal arm 23 coming radially into abutment on the rim 13 of the upstream nozzle 9. A rotational-coupling member 24 is fixed to the internal arm 23 and is engaged in the recess 12 in the external platform 10 of the upstream nozzle 9, so as to rotationally immobilise the sector 15 with respect to the upstream nozzle 9 and casing
2.
The upstream nozzle 9 is thus fixed to the upstream flange 4 by means of the upstream fixing member 21. This member also makes it possible to fix the support 20 to the upstream flange 4.
An annular fixing member with a U-shaped cross section or localised members such as hooks 25 with a U-shaped cross section are fixed at an axially middle zone of the support 20, radially outside said support 20. Said fixing members 25, which will be referred to hereinafter as downstream fixing members, comprise a radially external arm 26 and a radially internal arm 27, able to come into abutment respectively on the radially external surface and the radially internal surface of the downstream flange 5.
The downstream fixing members 25 thus make it possible to fix the support 20 to the downstream flange 5 of the casing 2.
The turbine 1 further comprises a rotor wheel comprising a disc 28 (figure 2) at the periphery of which blades 29 are mounted, the radially external periphery of each blade comprises a platform 30 comprising a first wiper 31, axially central, and two second wipers 32 offset axially on either side of the first wiper 31. The first and second wipers 31,32 extend radially outwards, the first wiper 31 extending radially outwards with respect to the second wipers 32. The first wiper 31 is engaged in the first group 17, the second wipers 32 being engaged in the second grooves 19.
The axial dimension of the grooves 17, 19 allows a movement or an uncertainty of axial positioning of the rotor wheel, and therefore of the wipers 31, 32, with respect to the casing 2, such uncertainty being able to be due to the manufacturing or assembly tolerances as well as to mechanical and/or thermal stresses in operation.
The assembly of such a turbine 1 is carried out as follows.
First of all the upstream nozzle 9 is mounted inside the casing 2, on the one hand, and the sectors 15 are mounted around the blades 29 so as to form the ring 14 made from abradable material.
The assembly comprising the rotor wheel comprising the disc 28 and the blades 29, as well as the ring 14 formed by said sectors 15, is next engaged axially inside the casing 2, so that the fixing members 21 are engaged axially on the upstream flange 4 and on the rims 13 of the upstream nozzle 9, and so that the downstream fixing members 25 are engaged axially on the downstream flange 5, thus providing the fixing of both the upstream nozzle 9 and the various sectors 15 on the casing 2.
Figure 6 shows a variant embodiment that differs from the one disclosed above in that the ring formed by the blocks 16 has no second grooves 19, the second wipers 32 coming opposite the radially internal cylindrical surfaces 18 of the blocks 16 of abradable material.
Figures 7 and 13 illustrate the various steps of assembling a turbine 100 according to another embodiment of the invention. In this embodiment, the turbine 100 comprises a fixed casing 102, having a frustoconical wall 103 the axis of which corresponds to the axis of the turbine engine and from which flanges referenced 104, 105, 106, 107 from upstream to downstream extend radially inwards. The terms upstream and downstream are defined with reference to the direction of flow of the gas flow in the turbine 100, that is to say from left to right in figure 9.
Each flange 104, 105, 106, 107 comprises a first annular part 108 extending radially inwards from the frustoconical wall 103, and a second cylindrical part 109 extending in the downstream direction. The flanges 104, 105, 106, 107 are offset axially from one another, from upstream to downstream, and radially from inside to outside.
In other words:
- the axial part 109 of the flange 104 is thus situated radially inside the axial part 109 of the flange 105 situated directly downstream of the flange 104,
- the axial part 109 of the flange 105 is thus situated radially inside the axial part 109 of the flange 106 situated directly downstream of the flange 105,
- the axial part 109 of the flange 106 is thus situated radially inside the axial part 109 of the flange 107 situated directly downstream of the flange 106.
As can be seen more clearly in figure 13, the turbine comprises an upstream ring 114 and a downstream ring 114’. Each ring 114, 114’ comprises an abradable material, mounted fixedly on the casing 102 and formed by a plurality of angular sectors 115, 115’ (figure 7, figure 11), contiguous, identical and distributed over the entire circumference. Each sector 115, 115’ comprises a block of abradable material 116, 116’.
The ring formed by the various blocks 116, 116’ of abradable material comprises a first annular groove 117, 117’, having a first radial dimension or depth and emerging at a cylindrical radially internal surface 118 (figure 7), 118’ (figure 11) of the ring, and two second annular grooves 119, 119’, each having a second radial dimension or depth and emerging at said radially internal surface 118, 118’.
The first radial dimension is for example between 0.5 and 5 mm.
The second radial dimension is for example between 0.5 and mm.
The two second grooves 119, 119’ are offset axially on either side of the first groove 117, 117’.
The external surface of the block 116, 116’ of each sector is fixed to an annular-shaped support 120, 120’. The support may be cylindrical, as in the case of the support 120’ of the downstream part of the turbine 100. The support may also comprise at least one frustoconical part, as in the case of the support 120 of the upstream part of the turbine 100.
An annular fixing member 121, 121’ with a U-shaped cross section is fixed at the upstream end of the support 120, 120’, radially inside said support 120, 120’. Said upstream fixing member 121,121’ comprises a radially external arm 122, 122’ (figure 7, figure 11), coming radially into abutment on the external surface of the second part 109 of the corresponding flange 104, 106, and a radially internal arm 123, 123’, coming radially into abutment on a rim 113’ of the external platform 110’ of a nozzle 109’ situated upstream. A rotational coupling member 124’ is fixed to the internal arm 123’ and is engaged in a recess 112’ of the external platform 110’ of the nozzle 109’, so as to rotationally immobilise the sector of the ring 114’ with respect to the nozzle 109’ and casing 102.
As before, each nozzle 109’ comprises a radially internal platform (not visible), a radially external platform 110’ and fixed vanes 111’ connecting said platforms.
The nozzle 109’ is thus fixed to the corresponding flange 106 by means of the fixing member 121’. This member 121’ also makes it possible to fix the support 120’ to the flange 106.
The external platform 110’ of the nozzle 109’ comprises moreover, at its upstream end, a radially external rim 133’ and a radially internal rim 134’, as well as a recess 135’ emerging towards the upstream end and situated radially between the rims 133’ and 134’.
An annular fixing member with a U-shaped cross section or localised members such as hooks 125, 125’ with a U-shaped cross section are fixed at a downstream zone of the support 120 or at an axially middle zone of the support 120’, radially outside the support 120, 120’. Said fixing members 125, 125’, which will be referred to hereinafter as downstream fixing members, each comprise a radially external arm 126, 126’ (figure 7, figure 11) and a radially internal arm 127’ secured to the support 120, 120’ or which may be coincident with the support 120, 120’, said external and internal arms being able to come into abutment respectively on the radially external surface and radially internal surface of the corresponding flange 105, 107.
The downstream fixing members 125, 125’ thus make it possible to fix the support 120, 120’ to the corresponding flange 105, 107 of the casing 102.
Moreover, the support 120 of each sector 115 is extended in the downstream direction by at least one finger 136 engaged by complementarity of shapes in the recess 135’ of the nozzle 109’ so as to effect a rotational coupling of the nozzle 109’ and sector 115 concerned.
Finally, the block of abradable material 116 of each sector 114 comprises an indentation at its downstream end, delimiting a shoulder 137.
The turbine 100 further comprises rotor wheels each comprising a disc at the periphery of which blades 129, 129’ are mounted. The radially external periphery of each blade 129, 129’ comprises a platform 130, 130’ comprising a first wiper 131, 131’, axially central, and two second wipers 132, 132’ offset axially on either side of the first wiper 131, 131’ (figure 7, figure 11). The first and second wipers 131, 131’, 132, 132’ extend radially outwards, the first wiper 131, 131’ extending radially outwards with respect to the second wipers 132, 132’. The first wiper 131, 131’ is engaged in the first groove 117, 117’, the second wipers 132, 132’ being engaged in the second grooves 119, 119’ (figure 13).
As before, the axial dimension of the grooves 117, 117’, 119, 119’ allows a movement or uncertainty of axial positioning of the rotor wheel, and therefore of the wipers 131, 131’, 132, 132’ with respect to the casing 102, such uncertainty being able to be due to the manufacturing and assembly tolerances as well as to mechanical and/or thermal stresses in operation.
The assembly of such a turbine 100 is carried out as follows.
First of all an upstream nozzle (not shown in figures 7 to 13) is mounted in said casing 102, on the one hand, and the sectors 115 are mounted around the blades 129 so as to form the ring 114 made from abradable material, on the other hand (figure 7).
The assembly comprising the upstream rotor wheel comprising the disc and the blades 129, as well as the ring 114 formed by said sectors 115, is next engaged axially from downstream to upstream inside the casing 102, so that the fixing members 121 are engaged axially on the flange 104 and on the corresponding rims of the upstream nozzle, and so that the downstream fixing members 125 are engaged axially on the flange 105, thus providing the fixing both of the upstream nozzle and of the various sectors 115 on the casing 102 (figure 8).
The downstream nozzle 109’ is next mounted inside the casing 102, the radially external rim 133’ coming to be housed outside the radially external arm of the hook 125, the radially internal rim 134’ coming to be housed inside the shoulder 137 (figures 9 and 10). Moreover, the finger 136 comes to be housed in the indentation 135’ and an anti-rotation finger 138 mounted in the casing 102 comes to be housed in an indentation 139’ in the nozzle 109’ so as to prevent rotation of the nozzle 109’ with respect to the casing 102, and therefore also rotation of the sectors 115 with respect to the casing 102, through the fingers 136.
The assembly comprising the downstream rotor wheel comprising the disc and the blades 129’, as well as the ring 114’ formed by said sectors 115’, is next engaged axially from downstream to upstream inside the casing 102, so that the fixing members 121’ are engaged axially on the flange 106 and on the rims 113’ of the downstream nozzle 109’, and so that the downstream fixing members 125’ are engaged axially on the flange 107, thus providing the fixing both of the downstream nozzle and of the various sectors 115’ on the casing 102 (figures 11,12 and 13).
Whatever the embodiment of the invention, in each assembly step, the sectors 15, 115, 115’ are engaged axially in a solely axial direction, directed from downstream to upstream. This is allowed in particular by the configuration of the casing 2, 102, in particular by the positioning of the flanges 4, 5, 104, 105, 106, 107 with respect to one another, in particular by the radial offset thereof. It will be recalled in fact that the flanges are separated, from upstream to downstream, radially from inside to outside. This considerably facilitates the mounting of the sectors 15, 115, 115’ in the casing 2, 102.
Claims (12)
1. A turbine (1) for a turbine engine, in particular for an aircraft turbojet engine or turboprop engine, comprising a casing (2) and a rotor comprising blades (29), the radially external periphery of which comprises at least one first wiper (31) extending radially outwards, sealing means extending radially around the blades (29) and comprising a ring (14) made from abradable material, the radially external ends of the first wipers (31) being engaged in a groove (17) in said ring (14) made from abradable material so as to form a seal of the labyrinth type, characterised in that said ring (14) is formed by a plurality of contiguous annular sectors (15), each ring sector (15) comprising at least one fixing member (21,25) cooperating with at least one complementary attachment flange (4, 5) of the casing (2) so as to provide the mounting of each sector (15) on the casing (2) by axial movement of said sector (15) with respect to the casing (2), the casing being configured so as to allow the mounting of the sectors (15) in the casing, solely by axial movement of said sectors (15).
2. A turbine (1) according to claim 1, characterised in that each flange (4, 5) comprises a first part (6) extending radially from a cylindrical or frustoconical wall (3) of the casing (2), and a second part (7) extending axially, cooperating with the fixing member (21, 25) of the corresponding ring sector (15).
3. A turbine (1) according to claim 1 or claim 2, characterised in that each fixing member (21, 25) comprises a roughly U-shaped section comprising arms (22, 23; 26, 27) extending axially and separated radially from each other, coming into engagement on either side of an axial part (7) of the complementary attachment flange (4, 5).
4. A turbine (1) according to any of claims 1 to 3, characterised in that it comprises at least one first fixing member (21) and at least one second fixing member (25), offset axially with respect to each other, able to cooperate respectively with a first flange (4) and a second flange (5) of the casing (2).
5. A turbine (1) according to any of claims 1 to 4, characterised in that each ring sector (15) comprises a block (16) of abradable material fixed to a support (20), each fixing member (21, 25) being formed by said support (20) or fixed to said support (20).
6. A turbine (1) according to any of claims 1 to 5, characterised in that each blade (29) comprises at least one first wiper (31) extending radially and at least one second wiper (32) extending radially outwards with respect to the first wiper (31), the first wiper (31) and the second wiper (32) being offset axially with respect to each other.
7. A turbine (1) according to claim 6, characterised in that the first wiper (31) is engaged in a first groove (17) in the corresponding ring sector (15), the second wiper (32) being engaged in a second groove (19) in the ring sector (15).
8. A turbine (1) according to claim 6, characterised in that the first wiper (31) is engaged in a first groove (19) in the corresponding ring sector (15), the radially external end of the second wiper (32) being situated in the vicinity of a surface (18) in a portion of a cylinder of the ring sector (15).
9. A turbine (1) according to any of claims 1 to 8, characterised in that it comprises a nozzle (9), comprising a radially external platform (10), in abutment on a flange (4) of the casing (2), the sector (15) comprising a fixing member (21) fixing the external platform (10) of the nozzle (9) on the corresponding flange (4) of the casing (2), while fixing the sector (15) to said flange (4).
10. A turbine according to any of claims 1 to 9, characterised in that it comprises a first blade stage (129) and a second blade stage (129’) surrounded respectively by a first ring (114) and a second ring (114’) made from abradable material and formed from sectors (115, 115’) so as to form a first and second labyrinth seal, the casing (102) being configured so as to allow the mounting of the sectors (115, 115’) in the casing (102), solely by axial movement of said sectors (115, 115’).
11. A method for assembling a turbine (1) according to any of claims 1 to 10, characterised in that it comprises the steps consisting of:
- mounting the sectors (15) around the blades (29) so as to form the ring (14) made from abradable material,
- axially engaging the assembly comprising in particular the blades (29) and said sectors (15) in the casing (2), so that the fixing members (21, 25) of the sectors (15) cooperate with the flanges (4, 5) so as to provide the fixing of said sectors (15) in the casing (2), around the blades (29).
12. An assembly method according to claim 11, characterised in that it comprises the steps consisting of:
- mounting a first ring (114) of sectors (115) around a first blade stage (129), and axially engaging the assembly comprising in particular said blades (129) and said sectors (115) in the casing (102), so that the fixing members (121, 125) of the sectors (115) cooperate with the corresponding flanges (104, 105) so as to provide the fixing of said sectors (115) in the casing (102), around the blades (129),
- mounting a second ring (114’) of sectors (115’) around a second blade stage (129’), and axially engaging the assembly comprising in particular said blades (129’) and said sectors (115’) in the casing (102), so that the fixing members (121’, 125’) of the sectors (115’) cooperate with the corresponding flanges (106, 107) so as to provide the fixing of said sectors (115’) in the casing (102), around the blades (129’).
ytAjg/ZW»1
Intellectual
Property
Office
Application No: GB1718654.5 Examiner: Adrian Mooney
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR1661045A FR3058756B1 (en) | 2016-11-15 | 2016-11-15 | TURBINE FOR TURBOMACHINE |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| GB201718654D0 GB201718654D0 (en) | 2017-12-27 |
| GB2558071A true GB2558071A (en) | 2018-07-04 |
| GB2558071B GB2558071B (en) | 2021-07-14 |
Family
ID=58401660
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB1718654.5A Active GB2558071B (en) | 2016-11-15 | 2017-11-10 | Turbine for turbine engine |
Country Status (3)
| Country | Link |
|---|---|
| US (1) | US10907505B2 (en) |
| FR (1) | FR3058756B1 (en) |
| GB (1) | GB2558071B (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR3065482B1 (en) * | 2017-04-20 | 2019-07-05 | Safran Aircraft Engines | SEAL RING MEMBER FOR TURBINE COMPRISING A CAVITY INCLINED IN ABRADABLE MATERIAL |
| FR3083563B1 (en) * | 2018-07-03 | 2020-07-24 | Safran Aircraft Engines | AIRCRAFT TURBOMACHINE SEALING MODULE |
| FR3103209B1 (en) * | 2019-11-20 | 2022-05-27 | Safran Aircraft Engines | Labyrinth seal comprising a sliding abradable element |
| US11326462B2 (en) * | 2020-02-21 | 2022-05-10 | Mechanical Dynamics & Analysis Llc | Gas turbine and spacer disk for gas turbine |
| US11692490B2 (en) * | 2021-05-26 | 2023-07-04 | Doosan Heavy Industries & Construction Co., Ltd. | Gas turbine inner shroud with abradable surface feature |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0140736A2 (en) * | 1983-09-21 | 1985-05-08 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." | Connection and sealing of stator blade sections of a turbine |
| US20130149125A1 (en) * | 2010-10-29 | 2013-06-13 | Mitsubishi Heavy Industries, Ltd. | Turbine and method for manufacturing turbine |
| FR3036435A1 (en) * | 2015-05-22 | 2016-11-25 | Herakles | TURBINE RING ASSEMBLY |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0844369B1 (en) * | 1996-11-23 | 2002-01-30 | ROLLS-ROYCE plc | A bladed rotor and surround assembly |
| JP4285134B2 (en) * | 2003-07-04 | 2009-06-24 | 株式会社Ｉｈｉ | Shroud segment |
| US7334984B1 (en) * | 2003-12-24 | 2008-02-26 | Heico Corporation | Turbine shroud assembly with enhanced blade containment capabilities |
| US7287956B2 (en) * | 2004-12-22 | 2007-10-30 | General Electric Company | Removable abradable seal carriers for sealing between rotary and stationary turbine components |
| FR2989724B1 (en) * | 2012-04-20 | 2015-12-25 | Snecma | TURBINE STAGE FOR A TURBOMACHINE |
| EP2984296B1 (en) * | 2013-04-12 | 2020-01-08 | United Technologies Corporation | Blade outer air seal with secondary air sealing |
| FR3007065B1 (en) * | 2013-06-14 | 2017-11-10 | Snecma | ABRADABLE RING FOR TURBOMACHINE |
-
2016
- 2016-11-15 FR FR1661045A patent/FR3058756B1/en active Active
-
2017
- 2017-11-10 GB GB1718654.5A patent/GB2558071B/en active Active
- 2017-11-14 US US15/812,117 patent/US10907505B2/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0140736A2 (en) * | 1983-09-21 | 1985-05-08 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." | Connection and sealing of stator blade sections of a turbine |
| US20130149125A1 (en) * | 2010-10-29 | 2013-06-13 | Mitsubishi Heavy Industries, Ltd. | Turbine and method for manufacturing turbine |
| FR3036435A1 (en) * | 2015-05-22 | 2016-11-25 | Herakles | TURBINE RING ASSEMBLY |
Also Published As
| Publication number | Publication date |
|---|---|
| FR3058756A1 (en) | 2018-05-18 |
| US10907505B2 (en) | 2021-02-02 |
| US20180156070A1 (en) | 2018-06-07 |
| FR3058756B1 (en) | 2020-10-16 |
| GB201718654D0 (en) | 2017-12-27 |
| GB2558071B (en) | 2021-07-14 |
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